Symmetric fuel injection for turbine combustor
A fuel injection system comprises a combustor liner, an air tube, a fuel manifold and a fuel injector. The combustor liner defines primary and secondary combustion zones. The air tube extends through the combustor liner along an axis to an exit aperture inside the combustor. The fuel manifold is pos...
Gespeichert in:
| Hauptverfasser: | , |
|---|---|
| Format: | Patent |
| Sprache: | eng |
| Schlagworte: | |
| Online-Zugang: | Volltext bestellen |
| Tags: |
Tag hinzufügen
Keine Tags, Fügen Sie den ersten Tag hinzu!
|
| container_end_page | |
|---|---|
| container_issue | |
| container_start_page | |
| container_title | |
| container_volume | |
| creator | PEFFLEY JAMES MEHRING CARSTEN RALF |
| description | A fuel injection system comprises a combustor liner, an air tube, a fuel manifold and a fuel injector. The combustor liner defines primary and secondary combustion zones. The air tube extends through the combustor liner along an axis to an exit aperture inside the combustor. The fuel manifold is positioned proximate the combustor line to deliver fuel through the air tube to the primary and secondary combustion zones. The fuel injector is coupled to the fuel manifold and positioned to inject the fuel along an axis of the air tube, such that the fuel has a substantially symmetric distribution at the exit aperture. |
| format | Patent |
| fullrecord | <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_US9062609B2</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>US9062609B2</sourcerecordid><originalsourceid>FETCH-epo_espacenet_US9062609B23</originalsourceid><addsrcrecordid>eNrjZNALrszNTS0pykxWSCtNzVHIzMtKTS7JzM9TSMsvUigpLUrKzEtVSM7PTSotLskv4mFgTUvMKU7lhdLcDApuriHOHrqpBfnxqcUFicmpeakl8aHBlgZmRmYGlk5GxkQoAQDegirR</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>Symmetric fuel injection for turbine combustor</title><source>esp@cenet</source><creator>PEFFLEY JAMES ; MEHRING CARSTEN RALF</creator><creatorcontrib>PEFFLEY JAMES ; MEHRING CARSTEN RALF</creatorcontrib><description>A fuel injection system comprises a combustor liner, an air tube, a fuel manifold and a fuel injector. The combustor liner defines primary and secondary combustion zones. The air tube extends through the combustor liner along an axis to an exit aperture inside the combustor. The fuel manifold is positioned proximate the combustor line to deliver fuel through the air tube to the primary and secondary combustion zones. The fuel injector is coupled to the fuel manifold and positioned to inject the fuel along an axis of the air tube, such that the fuel has a substantially symmetric distribution at the exit aperture.</description><language>eng</language><subject>AIR INTAKES FOR JET-PROPULSION PLANTS ; BLASTING ; BURNERS ; CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION ; COMBUSTION APPARATUS ; COMBUSTION ENGINES ; COMBUSTION PROCESSES ; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ; GAS-TURBINE PLANTS ; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC ; GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS ; GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS ; HEATING ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; LIGHTING ; MECHANICAL ENGINEERING ; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS ; TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE ; WEAPONS</subject><creationdate>2015</creationdate><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><linktohtml>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20150623&DB=EPODOC&CC=US&NR=9062609B2$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25543,76293</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20150623&DB=EPODOC&CC=US&NR=9062609B2$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>PEFFLEY JAMES</creatorcontrib><creatorcontrib>MEHRING CARSTEN RALF</creatorcontrib><title>Symmetric fuel injection for turbine combustor</title><description>A fuel injection system comprises a combustor liner, an air tube, a fuel manifold and a fuel injector. The combustor liner defines primary and secondary combustion zones. The air tube extends through the combustor liner along an axis to an exit aperture inside the combustor. The fuel manifold is positioned proximate the combustor line to deliver fuel through the air tube to the primary and secondary combustion zones. The fuel injector is coupled to the fuel manifold and positioned to inject the fuel along an axis of the air tube, such that the fuel has a substantially symmetric distribution at the exit aperture.</description><subject>AIR INTAKES FOR JET-PROPULSION PLANTS</subject><subject>BLASTING</subject><subject>BURNERS</subject><subject>CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION</subject><subject>COMBUSTION APPARATUS</subject><subject>COMBUSTION ENGINES</subject><subject>COMBUSTION PROCESSES</subject><subject>CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS</subject><subject>GAS-TURBINE PLANTS</subject><subject>GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC</subject><subject>GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS</subject><subject>GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS</subject><subject>HEATING</subject><subject>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</subject><subject>LIGHTING</subject><subject>MECHANICAL ENGINEERING</subject><subject>TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS</subject><subject>TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2015</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZNALrszNTS0pykxWSCtNzVHIzMtKTS7JzM9TSMsvUigpLUrKzEtVSM7PTSotLskv4mFgTUvMKU7lhdLcDApuriHOHrqpBfnxqcUFicmpeakl8aHBlgZmRmYGlk5GxkQoAQDegirR</recordid><startdate>20150623</startdate><enddate>20150623</enddate><creator>PEFFLEY JAMES</creator><creator>MEHRING CARSTEN RALF</creator><scope>EVB</scope></search><sort><creationdate>20150623</creationdate><title>Symmetric fuel injection for turbine combustor</title><author>PEFFLEY JAMES ; MEHRING CARSTEN RALF</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_US9062609B23</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2015</creationdate><topic>AIR INTAKES FOR JET-PROPULSION PLANTS</topic><topic>BLASTING</topic><topic>BURNERS</topic><topic>CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION</topic><topic>COMBUSTION APPARATUS</topic><topic>COMBUSTION ENGINES</topic><topic>COMBUSTION PROCESSES</topic><topic>CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS</topic><topic>GAS-TURBINE PLANTS</topic><topic>GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC</topic><topic>GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS</topic><topic>GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS</topic><topic>HEATING</topic><topic>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</topic><topic>LIGHTING</topic><topic>MECHANICAL ENGINEERING</topic><topic>TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS</topic><topic>TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>PEFFLEY JAMES</creatorcontrib><creatorcontrib>MEHRING CARSTEN RALF</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>PEFFLEY JAMES</au><au>MEHRING CARSTEN RALF</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Symmetric fuel injection for turbine combustor</title><date>2015-06-23</date><risdate>2015</risdate><abstract>A fuel injection system comprises a combustor liner, an air tube, a fuel manifold and a fuel injector. The combustor liner defines primary and secondary combustion zones. The air tube extends through the combustor liner along an axis to an exit aperture inside the combustor. The fuel manifold is positioned proximate the combustor line to deliver fuel through the air tube to the primary and secondary combustion zones. The fuel injector is coupled to the fuel manifold and positioned to inject the fuel along an axis of the air tube, such that the fuel has a substantially symmetric distribution at the exit aperture.</abstract><oa>free_for_read</oa></addata></record> |
| fulltext | fulltext_linktorsrc |
| identifier | |
| ispartof | |
| issn | |
| language | eng |
| recordid | cdi_epo_espacenet_US9062609B2 |
| source | esp@cenet |
| subjects | AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING BURNERS CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION COMBUSTION APPARATUS COMBUSTION ENGINES COMBUSTION PROCESSES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE WEAPONS |
| title | Symmetric fuel injection for turbine combustor |
| url | https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2025-01-23T19%3A58%3A12IST&url_ver=Z39.88-2004&url_ctx_fmt=infofi/fmt:kev:mtx:ctx&rfr_id=info:sid/primo.exlibrisgroup.com:primo3-Article-epo_EVB&rft_val_fmt=info:ofi/fmt:kev:mtx:patent&rft.genre=patent&rft.au=PEFFLEY%20JAMES&rft.date=2015-06-23&rft_id=info:doi/&rft_dat=%3Cepo_EVB%3EUS9062609B2%3C/epo_EVB%3E%3Curl%3E%3C/url%3E&disable_directlink=true&sfx.directlink=off&sfx.report_link=0&rft_id=info:oai/&rft_id=info:pmid/&rfr_iscdi=true |